EP1003241B1 - Antennenanordnung für Satelliten auf niedriger und mittlerer Umlaufbahn - Google Patents

Antennenanordnung für Satelliten auf niedriger und mittlerer Umlaufbahn Download PDF

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Publication number
EP1003241B1
EP1003241B1 EP99123001A EP99123001A EP1003241B1 EP 1003241 B1 EP1003241 B1 EP 1003241B1 EP 99123001 A EP99123001 A EP 99123001A EP 99123001 A EP99123001 A EP 99123001A EP 1003241 B1 EP1003241 B1 EP 1003241B1
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EP
European Patent Office
Prior art keywords
lens
feed
beams
antenna configuration
diameter
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Expired - Lifetime
Application number
EP99123001A
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English (en)
French (fr)
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EP1003241A1 (de
Inventor
Sudhakar Rao
Philip H. Law
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
DirecTV Group Inc
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Hughes Electronics Corp
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    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q3/00—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system
    • H01Q3/26—Arrangements for changing or varying the orientation or the shape of the directional pattern of the waves radiated from an antenna or antenna system varying the relative phase or relative amplitude of energisation between two or more active radiating elements; varying the distribution of energy across a radiating aperture
    • H01Q3/2605—Array of radiating elements provided with a feedback control over the element weights, e.g. adaptive arrays
    • H—ELECTRICITY
    • H01—ELECTRIC ELEMENTS
    • H01Q—ANTENNAS, i.e. RADIO AERIALS
    • H01Q19/00—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic
    • H01Q19/06—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using refracting or diffracting devices, e.g. lens
    • H01Q19/08—Combinations of primary active antenna elements and units with secondary devices, e.g. with quasi-optical devices, for giving the antenna a desired directional characteristic using refracting or diffracting devices, e.g. lens for modifying the radiation pattern of a radiating horn in which it is located

Definitions

  • the present invention relates to space and communications satellites, and more particularly, to an antenna configuration for a multiple beam satellite, suitable for being operated in low or medium earth orbits (LEO/MEO).
  • LEO/MEO low or medium earth orbits
  • Satellites in geostationary orbits have been widely preferred because of the economic advantages afforded by such orbits.
  • GSO's geostationary orbits
  • These satellites are always "in view” at all locations within their service areas, so their utilization efficiency is effectively 100 percent.
  • Antennas on earth need be aimed at a GSO satellite only once; no tracking system is required.
  • LEO's low earth orbits
  • MEO's medium earth orbits
  • Ka and V-bands up to approximately 50 GHz
  • a host of proposed LEO and MEO systems exemplify this direction.
  • a LEO-System is e.g. disclosed in FR-A-2 762 936.
  • the beams are required to be circular close to the center of coverage and elliptical at the edge of coverage for a uniform cell size on the earth.
  • the different beam requirements increase the complexity of the beam-forming circuitry.
  • signals from each feed are divided into a number of beam portions. Each portion is amplitude and phase weighted using variable active components. The beam portions are then combined to form beams.
  • the feed network for the known systems becomes quite complicated because a large dividing network, a large combining network and large number of variable attenuators and/or variable phase shifters are required.
  • the number of variable attenuators is the product of the number of beams and the number of elements per beam.
  • the beam-forming network is complex and thus the weight and size and power consumption are relatively high. It would therefore be desirable to reduce the complexity of the beam-forming network and therefore reduce the size, weight and power consumption of the satellite.
  • the present invention is an antenna for a satellite that may use only one feed per beam. It does not require a beam former to generate various size beams.
  • the satellite antenna configuration includes a dielectric lens and a plurality of feed horns positioned appropriately with respect to the lens.
  • the lens has a first surface and a second surface.
  • the lens is common to all beams and is shaped such that it converts an incident spherical wavefront from the feeds to a planar wave front at the exit aperture of the lens.
  • the plurality of feed horns are disposed upon a curved surface. Each of the plurality of feed horns generates a primary beam on the inner surface of the lens, which is phase-corrected by the lens surfaces and creates a secondary beam from the lens outer surface onto the earth.
  • the amplitude and phase distributions at the outer surface of the lens control the secondary beam size and shape.
  • the desired amplitude and phase distributions are achieved by controlling the feed size, its location relative to the lens, and the shape of the lens.
  • said plurality of feed horns have a center feed horn and an edge feed horn, wherein said center feed horn has a greater diameter than the edge feed horn.
  • One advantage of the invention is that the use of active components for amplitude and phase weightings is eliminated. Also, the number of uplink and downlink amplifiers is reduced.
  • Another advantage is that the present invention may also be applied to GEO satellites.
  • Network 14 may be formed of low earth orbit (LEO) satellites 16, medium earth orbit (MEO) 18 satellites, a GEO stationary orbit (GSO) satellite or any combination thereof.
  • LEO low earth orbit
  • MEO medium earth orbit
  • GSO GEO stationary orbit
  • Each satellite 12 projects a plurality of beams, one of which is shown at 22, to the surface of the earth.
  • Beams 22 may be used to transmit and receive communications from the earth's surface.
  • Beam 22 projects a footprint 24 onto the surface of the earth.
  • a beam layout 26 for a medium earth orbit or low earth orbit satellite of the present invention is shown.
  • a plurality of footprints 28 are labeled A, B, and C.
  • Each of the three footprints comes from three different lens apertures that are formed according to the present invention.
  • the footprints labeled A, the footprints labeled B, and the footprints labeled C originate from a respective antenna aperture.
  • an antenna 30 is illustrated for generating a plurality of beams.
  • a number of antennas 30 may be used to generate the beams.
  • three antennas 30 were used to generate the plurality of beams.
  • Each beam labeled A, B, and C originates from a respective antenna.
  • Antenna 30 has a lens 32, a plurality of antenna elements 34, and a feed network 36 coupled to antenna elements 34.
  • Lens 32 reshapes a beam of electromagnetic energy signals that is directed therethrough.
  • Lens 32 preferably has an outer surface 38 that is spherical and an inner surface 40, which is also curved.
  • Inner surface 40 has a curve shape so that an incident spherical wavefront distribution from antenna elements 34 is converted to a planar wavefront distribution at the output aperture of the lens. This allows the lens to transmit and receive a signal with a uniform phase distribution across a cross-section perpendicular to the longitudinal axis of the beam.
  • outer surface 38 of lens 32 is spherical and the inner surface 40 is shaped.
  • the inner surface of the lens may also be zoned to reduce the mass and minimize the coma errors for the scanned beams.
  • Lens 32 satisfies the so-called Abbe-Sine condition for scanned beams.
  • Both the inner and outer surfaces of the lens may be surface matched using circumferential slots to match the lens to free-space and to reduce the mass.
  • Antenna elements 34 are an array of feed horns 42 disposed about a curved surface 44. As will be further described below, curved surface 44 has a geometric relationship to lens 32. Feed horns 42 illustrated are arrayed in the azimuth and elevation planes.
  • Feed network 36 is coupled to each of the feed horns 42 and has a typical configuration for each antenna element 34.
  • Each feed horn 42 has a filter 46 used to reject either transmit or receive frequencies.
  • Filter 46 is coupled to a polarizer 48.
  • Polarizer 48 is used to generate different polarizations.
  • polarizer 48 may generate dual circular polarizations (left-hand and right-hand circular).
  • Polarizer 48 has two inputs consisting of two switches 47 and a redundant low noise amplifier 49. Thus, half of the total number of beams from each respective antenna 30 is oppositely polarized. Using two different polarizations increases the spectral reuse by two-fold.
  • Feed horns 42 have varying diameters.
  • the central feed horn has a diameter d 1 larger than the edge feed horn.
  • the diameters of the feed horns decrease moving from the center feed horn to the edge feed horn, which has a diameter d 2 . This allows the center beam to have a larger diameter.
  • lens 32 has a diameter of 16 inches and a focal length of 48 inches.
  • the relatively large F/D ratio minimizes the scan losses and reduces the cross-polar radiation from the lens.
  • the inner surface 40 of lens 32 has a shape to have an even phase distribution across the outer surface 38 of lens 32.
  • a feed network 36 is illustrated with respect to lens 32 and the earth's surface 50.
  • Lens 32 has a central point 52 located in the center of inner surface 40.
  • a center feed 54 generates a central beam 56 that has a center line 58.
  • Center feed 54 is located a distance ⁇ c distance away from inner surface 40 of lens 32.
  • Central beam 56 is directed from the central point 52.
  • Central beam 56 is focused by lens 32 to a displaced focal point instead of the real focus F.
  • the distance between curved surface 44 and lens 32 is the distance F-F D .
  • the distance by which the central beam feed is defocused is F D .
  • This formula is applicable to feeds along curve surface 44.
  • the desired quadratic phase distribution of the beams across the lens surface is achieved to broaden the beams.
  • the beam may also have a linear phase relationship with the outer surface 38 so that the beam is directed to appropriate locations on the earth.
  • curved surface 44 has generally two different curves.
  • the first curve 64 is located in the central portion of curved surface 44.
  • First curve 64 has a generally spherical cross section.
  • the curved surface 44 also has a second curved area 66 around the outer edge of curved surface 44 with feed locations defined by ⁇ e .
  • the desired phase distribution for each of the beams has two components: a linear phase distribution across the outer aperture plane of the lens to direct the beam to required location on the earth; and a quadratic phase distribution across the outer aperture plane of the lens to broaden the central beams.
  • the desired footprint of the beam on the earth's surface 50 is determined. This allows the focal length and the defocusing distance to be determined.
  • the angle ⁇ may also be determined as a function of the distance from the center feed.
  • the varying ⁇ c may be determined for each feed.
  • a typical value for "n" is 2.2.
  • Curved surface 44 may be determined by curve fitting a smooth curve between the central beam and an edge beam. The end values for the edge beams may be in the range of 1.8 to 2.2 in order to produce elliptical beams with minor axis of the ellipse rotated along the scan plane.
  • Each of the beams preferably is directed toward the central point 52 of the inner surface 40 of lens 32.
  • the diameter of the central beam is preferably about 56-60% larger than an edge beam. This geometry corresponds to the curvature of the earth wherein the edge beams are smaller due to the greater distance traveled.
  • a beam contour plot shows the variation of beam ellipticity and beam rotation by varying the "n" value.
  • the plot shows the beam pattern footprint with respect to azimuth degrees and elevation degrees.
  • FIG. 7 a plot of computed beam patterns of a low earth orbit satellite is illustrated.
  • the beam patterns illustrated are taken along the azimuth.
  • the computed patterns use a very accurate ray tube analysis.
  • the beams overlap and become elliptical near the edge of the coverage.
  • Figure 8 is a plot of computed beam contour versus axes degrees for the azimuth beams of Figure 7.
  • plots of a central beam copolar and cross-polar patterns are illustrated.
  • the plots are in azimuth degrees versus elevation degrees.
  • FIG 13 a layout of an antenna configuration 68 using three lenses 32 is illustrated in perspective.
  • the plurality of feed horns 42 are shown positioned with respect to lens 32.
  • a housing 70 is used to position lens 32 with respect to feed horns 42.
  • the generated beams from antenna configuration 48 form a beam pattern as shown in Figure 2.
  • Each lens 32 may have the same diameter.
  • FIG 14 a plot of scan angle versus required directivity is illustrated for the antenna configuration of Figure 13.
  • the edge of directivity coverage is about 4.7 dB higher than the central beam C directivity that compensates for the increased space attenuation for the edge beams.
  • antenna configuration 74 a variation of antenna configuration 68 of Figure 13 is shown as antenna configuration 74.
  • a plurality of lenses 76 having an equal diameter are shown.
  • Lenses 78 are smaller in diameter than lenses 76 in Figure 15. This configuration gives maximum flexibility for interleaving various size beams in forming the beam pattern.
  • the present invention may also be used for geostationary satellites with the exception that no defocusing for the feeed array is required. Also, the focal surface becomes almost spherical with each feed looking at the center of the lens. The lens is capable of scanning ⁇ 20 beam widths from the boresight with minimal scan loss.
  • the present invention relates to an antenna configuration suitable for LEO/MEO satellites includes a plurality of lenses whereby each lens has a plurality of feed horns positioned with respect to the lens.
  • the lens has a first surface and a second surface.
  • the plurality of feed horns is disposed upon a curved surface.
  • Each of the plurality of feed horns generates a beam that has a phase distribution.
  • the phase distributions have a predetermined phase relationship with a first surface and preferably the second surface. This allows the lens to transmit and receive a signal with desired phase distribution across a cross-section of the beam.
  • the beams from the plurality of lenses are interleaved on the ground to form a contiguous coverage with multiple overlapping spot-beams.
  • the invention greatly simplifies the feed array geometry by eliminating the beam-forming network. Also eliminated is the use of active components used inside the beam-forming network. this significantly reduces the weight and complexity of the satellite.

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  • Aerials With Secondary Devices (AREA)
  • Variable-Direction Aerials And Aerial Arrays (AREA)

Claims (8)

  1. Antennen-Anordnung mit:
    einer Linse (32), die eine erste Fläche (40) und eine zweite Fläche (38) aufweist; und
    einer Vielzahl von Hornstrahlern (42), wobei die Vielzahl von Hornstrahlern (42) auf einer gekrümmten Fläche (44) angeordnet sind, wobei jeder der Vielzahl von Hornstrahlern (42) einen Strahl mit einer Amplituden- und Phasen-Verteilung erzeugt, wobei die Verteilung eine bestimmte Phasenbeziehung zu der ersten Fläche (40) besitzt,
    dadurch gekennzeichnet, dass die Vielzahl von Hornstrahlern (42) einen mittleren Hornstrahler (54) mit einem ersten Durchmesser und einen Rand-Hornstrahler mit einem zweiten Durchmesser aufweist, wobei der erste Durchmesser des mittleren Hornstrahlers größer ist als der zweite Durchmesser.
  2. Antennen-Anordnung nach Anspruch 1, dadurch gekennzeichnet, dass der Strahl eine Amplituden-Verteilung hat, die in einer vorgegebenen Beziehung zu der zweiten Fläche (38) steht.
  3. Antennen-Anordnung nach Anspruch 1 oder 2, dadurch gekennzeichnet, dass die zweite Fläche (38) eine sphärische Form besitzt.
  4. Verwendung einer Antennen-Anordnung nach einem der Ansprüche 1 bis 3 in einem Satelliten-Netzwerk, wobei das Satelliten-Netzwerk aufweist:
    eine Vielzahl von Satelliten (12), wobei jeder Strahlformungselektronik aufweist; wobei die Vielzahl von Hornstrahlern (42) mit den Elektroniken elektrisch verbunden und mit der Linse (32) elektromagnetisch verbunden ist.
  5. Verwendung nach Anspruch 4, dadurch gekennzeichnet, dass die Linse (32) einen Abschnitt mit verminderter Dicke aufweist.
  6. Verwendung nach Anspruch 4 oder 5, dadurch gekennzeichnet, dass die Hornstrahler-Anordnungen (42) ein Horn (42), einen Polarisator (40) und ein mit einem Schalter (47) verbundenes Filter (46) aufweisen, wobei der Schalter mit einem Paar von Verstärkern (49) verbunden ist.
  7. Verwendung nach einem der Ansprüche 4 bis 6, dadurch gekennzeichnet, dass die Verstärker (49) rauscharme Verstärker aufweisen.
  8. Verwendung nach Ansprüchen 4 bis 7, gekennzeichnet durch eine Vielzahl von Linsen (32), wobei jede der Linsen (32) mit einer entsprechenden der Vielzahl von Hornstrahler-Anordnungen (42) verbunden ist.
EP99123001A 1998-11-20 1999-11-19 Antennenanordnung für Satelliten auf niedriger und mittlerer Umlaufbahn Expired - Lifetime EP1003241B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US196864 1998-11-20
US09/196,864 US6184838B1 (en) 1998-11-20 1998-11-20 Antenna configuration for low and medium earth orbit satellites

Publications (2)

Publication Number Publication Date
EP1003241A1 EP1003241A1 (de) 2000-05-24
EP1003241B1 true EP1003241B1 (de) 2003-02-26

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EP99123001A Expired - Lifetime EP1003241B1 (de) 1998-11-20 1999-11-19 Antennenanordnung für Satelliten auf niedriger und mittlerer Umlaufbahn

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US (2) US6184838B1 (de)
EP (1) EP1003241B1 (de)
DE (1) DE69905540T2 (de)
ES (1) ES2189338T3 (de)

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JP2004158911A (ja) 2002-11-01 2004-06-03 Murata Mfg Co Ltd セクタアンテナ装置および車載用送受信装置
US6961025B1 (en) * 2003-08-18 2005-11-01 Lockheed Martin Corporation High-gain conformal array antenna
US7193574B2 (en) * 2004-10-18 2007-03-20 Interdigital Technology Corporation Antenna for controlling a beam direction both in azimuth and elevation
US20070036353A1 (en) * 2005-05-31 2007-02-15 Interdigital Technology Corporation Authentication and encryption methods using shared secret randomness in a joint channel
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US10135137B2 (en) 2015-02-20 2018-11-20 Northrop Grumman Systems Corporation Low cost space-fed reconfigurable phased array for spacecraft and aircraft applications
WO2018037424A1 (en) * 2016-08-20 2018-03-01 Astrome Technologies Private Limited System and method for integrated optimization of design and performance of satellite constellations
CN112164885B (zh) * 2020-08-24 2022-10-14 西安空间无线电技术研究所 一种基于多馈源合成网络的幅相优化设计方法
CN112422170B (zh) * 2020-11-09 2022-10-28 大连交通大学 双频段射频设备近场自动化检测方法
CN112526512B (zh) * 2020-11-23 2022-07-22 电子科技大学 大功率大口径宽带毫米波空馈相控阵雷达系统及成像方法
USD1026428S1 (en) * 2021-11-10 2024-05-14 Puma SE Shoe

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Publication number Priority date Publication date Assignee Title
US8290215B2 (en) 2008-03-18 2012-10-16 Certusview Technologies, Llc Virtual white lines for delimiting planned excavation sites

Also Published As

Publication number Publication date
DE69905540D1 (de) 2003-04-03
DE69905540T2 (de) 2003-12-18
US6184838B1 (en) 2001-02-06
US6323815B1 (en) 2001-11-27
ES2189338T3 (es) 2003-07-01
EP1003241A1 (de) 2000-05-24

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